航空学报 > 2025, Vol. 46 Issue (15): 131142-131142   doi: 10.7527/S1000-6893.2024.31142

低压涡轮性能试验方法对效率测量精度的影响

赵磊(), 李杰, 许晶莹   

  1. 中国航发商用航空发动机有限责任公司 涡轮部,上海 200241
  • 收稿日期:2024-09-02 修回日期:2024-09-20 接受日期:2024-11-19 出版日期:2024-11-26 发布日期:2024-11-25
  • 通讯作者: 赵磊 E-mail:zhaolei@acae.com.cn
  • 基金资助:
    基础加强重点基础研发项目(请核实项目名称,并补充项目号)

Effects of low-pressure turbine rig test method on measurement accuracy of efficiency

Lei ZHAO(), Jie LI, Jingying XU   

  1. Turbine Department,AECC Commercial Aircraft Engine Co. ?,Ltd. ,Shanghai 200241,China
  • Received:2024-09-02 Revised:2024-09-20 Accepted:2024-11-19 Online:2024-11-26 Published:2024-11-25
  • Contact: Lei ZHAO E-mail:zhaolei@acae.com.cn

摘要:

性能试验是评价涡轮部件性能的最主要方式之一,其中效率测量精度对试验结果至关重要,但会受到诸多过程因素影响。基于低压涡轮性能试验,分析了进出口流场、封严气温度/流量、雷诺数、叶尖间隙、机械损失和效率定义对涡轮试验效率的影响,为涡轮性能试验、测试方案设计及试验数据分析提供参考。通过设置封严气温度与主流相同和在进气段外机匣铺设保温材料,可改善涡轮进口总温均匀性。涡轮出口测点周向分布与末级导叶相位强相关,出口探针周向布置应考虑末级导叶尾迹区与主流区的影响,否则可能带来超过0.1%的试验效率偏差。涡轮试验中必须考虑封严气与主流温比和流量比对涡轮效率的影响,并在试验过程中严格控制,低压涡轮封严气与主流温比每增加0.1,效率降低0.11%,流量比每增加1%,效率降低0.29%。雷诺数对低压涡轮效率影响显著,当采用固定出口总压的方案采集涡轮特性时,雷诺数变化导致的低压涡轮效率偏差可达到1%,应在自模区以上雷诺数开展涡轮特性试验,否则应保证不同试验状态点之间的雷诺数相等,或在试验后对雷诺数影响进行修正。此外,给出了叶尖间隙、机械损失和效率定义对试验效率的影响。

关键词: 涡轮, 涡轮试验, 效率, 封严气, 雷诺数, 叶尖间隙

Abstract:

Turbine rig test is a most important way to evaluate the turbine component performance. In the test, the accuracy of efficiency measurement is very important to the test results, but will be affected by many process factors. Based on the results of low-pressure turbine rig test, this paper analyzes the effects of inlet and outlet flow field, sealing flow temperature/mass flow rate, Reynolds number, tip clearance, mechanical loss and efficiency definition on turbine test efficiency, so as to provide reference for turbine performance test scheme design, instrumentation design and test data analysis. The uniformity of inlet total temperature can be improved by setting the sealing flow to have the same temperature as the main flow and covering the inlet outer casing with thermal insulation material during test. The circumferential distribution of the turbine exit measurement points is strongly correlated with the phase of the last guide vane. The circumferential arrangement of the exit probe should consider the influences of the wake and main flow regions of the last guide vane; otherwise, an efficiency deviation exceeding 0.1% may occur. The influences of the sealing flow temperature ratio and flow ratio on the turbine efficiency must be considered and strictly controlled in the turbine test. For a low-pressure turbine, the efficiency decreases by 0.11% with 0.1 increase in the seal air temperature ratio, and by 0.29% with 1% increase in the mass flow rate. The Reynolds number has a significant impact on the efficiency of the low-pressure tur-bine. When collecting turbine map data by using the scheme with a fixed exit total pressure, the difference in low-pressure turbine efficiency caused by change of Reynolds number can reach 1%. Turbine map tests should be conducted at the Reynolds number that is above the self-simulation region or is equal for different test conditions, or the effect of Reynolds number could be corrected after the test. In addition, this paper also shows the effect of blade tip clearance, mechanical losses, and efficiency definition on test efficiency.

Key words: turbine, rig test, efficiency, sealing flow, Reynolds number, tip clearance

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